US9856795B2 - Gas turbine system, controller, and gas turbine operation method - Google Patents

Gas turbine system, controller, and gas turbine operation method Download PDF

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US9856795B2
US9856795B2 US14/760,787 US201414760787A US9856795B2 US 9856795 B2 US9856795 B2 US 9856795B2 US 201414760787 A US201414760787 A US 201414760787A US 9856795 B2 US9856795 B2 US 9856795B2
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fuel
gas
composition
combustor
turbine
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US20150354466A1 (en
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Ryo Higashi
Yosuke Eto
Jun Sasahara
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Mitsubishi Power Ltd
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Mitsubishi Hitachi Power Systems Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/75—Application in combination with equipment using fuel having a low calorific value, e.g. low BTU fuel, waste end, syngas, biomass fuel or flare gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3013—Outlet pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow

Definitions

  • the present invention relates to a gas turbine system for supplying fuel gas to a combustor for combustion, a controller, and a gas turbine operation method.
  • a gas turbine having a compressor, a combustor, and a turbine
  • fuel gas and air compressed by the compressor are combusted in the combustor
  • the generated combustion gas is supplied to the turbine
  • the turbine is rotated.
  • this control system is referred to as “temperature adjustment control”.
  • the temperature of the combustion gas at the turbine inlet decreases from the turbine inlet temperature to the exhaust gas temperature due to adiabatic expansion, which is caused by passing through the turbine, and mixing with cooling air from the turbine vanes or the like.
  • the turbine expansion ratio which determines the temperature decrease amount of the combustion gas due to the adiabatic expansion
  • the turbine efficiency the specific heat ratio of the combustion gas
  • the volume of cooling air and the temperature of the cooling air which determine the temperature decrease amount due to mixing with the cooling air.
  • the combustion gas temperature is made equal to a predetermined value by controlling the fuel flow rate such that the measured turbine expansion ratio and exhaust gas temperature match a function of a given turbine expansion ratio and exhaust gas temperature.
  • the above-mentioned compressor exhaust air pressure is generally used in place of the turbine expansion ratio given that the inlet pressure of the turbine is equal to the compressor exhaust air pressure apart from the combustor pressure loss and that the outlet pressure of the turbine is equal to the atmospheric pressure (approximately 1 atm) apart from the exhaust pressure loss.
  • Patent Document 1 discloses a gas turbine combustion temperature control method which controls combustion temperature by measuring the discharged air pressure of a gas turbine compressor and a gas turbine exhaust gas temperature, and controlling a gas turbine fuel flow rate on the basis of these measured values.
  • This method includes detecting a calorific value of the gas turbine fuel, calculating changes in the exhaust gas temperature characteristics with respect to the discharged air pressure of the gas turbine compressor using the detected value of the calorific value, correcting the exhaust gas temperature characteristics using the calculated value, comparing the corrected value and an actual measured value of the exhaust gas temperature, and adjusting the fuel flow rate such that the difference in the comparison is minimized.
  • Patent Document 1 Japanese Unexamined Patent Application Publication No. 563-183230A
  • the gas turbine combustion temperature control method aims to carry out temperature adjustment control by performing control by correcting the exhaust gas temperature characteristics using a calorific value of the gas turbine fuel such that the temperature of the combustion gas is equal to a predetermined temperature even when the fuel gas composition changes.
  • the temperature of the combustion gas it is not desirable for the temperature of the combustion gas to exceed the maximum allowable temperature of the gas turbine (over-firing) since the lifespan of the combustor or the turbine vanes will be shortened.
  • the gas turbine since it is not possible to control the combustion gas temperature with high precision, the gas turbine must be operated with the combustion gas temperature decreased from the maximum allowable temperature, and such an operation leads to decreases in the output or efficiency of the gas turbine.
  • the present invention solves the problems described above and an object of the present invention is to provide a gas turbine system, a controller, and a gas turbine operation method, whereby the combustion gas temperature of a gas turbine can be controlled and the risk that over-firing may occur can be reduced.
  • a gas turbine system includes a gas turbine having a compressor, a combustor, and a turbine, a fuel supply mechanism for supplying fuel to the combustor, a composition detection unit for detecting a composition of the fuel, and a controller for controlling a flow rate of the fuel supplied from the fuel supply mechanism to the combustor, on the basis of a function of an exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine.
  • the controller calculates a specific heat ratio of a combustion gas from the composition of the fuel detected by the composition detection unit, corrects the function on the basis of the calculated specific heat ratio, and controls the flow rate of the fuel on the basis of the corrected function.
  • an exhaust gas temperature there are five main parameters which determine an exhaust gas temperature, which are the turbine expansion ratio, the turbine efficiency, the specific heat ratio of the combustion gas, the volume of the cooling air, and the temperature of the cooling air.
  • the composition of the turbine fuel gas changes, the relationship between the turbine expansion ratio and the exhaust gas temperature shifts from a reference state due to changes mainly in the specific heat ratio of the combustion gas out of these parameters. Therefore, it is possible to control the temperature of the combustion gas of the combustor with higher precision by correcting the function of the exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or the expansion ratio of the turbine on the basis of the specific heat ratio of the combustion gas, and adjusting the feed rate of the fuel gas on the basis of the correction result.
  • the combustion gas temperature of the gas turbine can be controlled, it is possible to reduce the risk that over-firing may occur.
  • the temperature of the combustion gas of a combustor can be controlled with high precision and the risk that over-firing may occur can be reduced, it is possible to set the temperature of the combustion gas of the combustor to a higher temperature and to extract the output more efficiently in the gas turbine.
  • the controller calculates the composition of the combustion gas on the basis of the composition of the fuel and an intake flow rate of the compressor, and calculates the specific heat ratio of the combustion gas on the basis of a ratio of each component contained in the combustion gas and the specific heat ratio of each component.
  • the controller calculates a bias value on the basis of the calculated specific heat ratio of the combustion gas and a specific heat ratio of a reference combustion gas, and controls the flow rate of the fuel supplied to the combustor on the basis of a function obtained by adding the calculated bias value to the function for the reference combustion gas.
  • a controller controls a fuel supply mechanism for supplying fuel to a combustor of a gas turbine.
  • the controller includes a composition information acquiring unit for acquiring composition information of fuel supplied to the combustor, and a fuel supply mechanism control unit for controlling a flow rate of the fuel supplied from the fuel supply mechanism to the combustor, on the basis of a function of an exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine.
  • the fuel supply mechanism control unit calculates a specific heat ratio of the combustion gas from the composition of the fuel, corrects the function on the basis of the calculated specific heat ratio, and controls the flow rate of the fuel on the basis of the corrected function and operation information.
  • the combustion gas temperature of the gas turbine can be controlled, it is possible to reduce the risk that over-firing may occur.
  • the temperature of the combustion gas of the combustor can be controlled with high precision and the risk that over-firing may occur can be reduced, it is possible to set the temperature of the combustion gas of the combustor to a higher temperature and to extract the output more efficiently in the gas turbine.
  • a gas turbine operation method of the present invention is an operation method for a gas turbine, the gas turbine including a compressor, a combustor, and a turbine, a fuel supply mechanism for supplying fuel to the combustor, and a composition detection unit for detecting a composition of the fuel.
  • the gas turbine operation method includes the steps of: calculating a specific heat ratio of a combustion gas from the composition of the fuel detected by the composition detection unit; correcting a function of an exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine, which is determined beforehand, on the basis of the calculated specific heat ratio; and controlling the fuel supplied from the fuel supply mechanism to the combustor on the basis of the corrected function.
  • the temperature of the combustion gas of the combustor can be controlled with high precision and the risk that over-firing may occur can be reduced, it is possible to set the temperature of the combustion gas of the combustor to a higher temperature and to extract the output more efficiently in the gas turbine.
  • the controller, and the gas turbine operation method of the present invention it is possible to control the temperature of a combustion gas so as to correspond to changes in the composition of a fuel gas supplied to a combustor. Accordingly, it is possible to reduce the risk that over-firing may occur. As a result, it is possible to set the temperature of the combustion gas of the combustor to a higher temperature, and to extract the output more efficiently in the gas turbine.
  • FIG. 1 is a schematic configuration diagram representing a gas turbine system of the present embodiment.
  • FIG. 2 is a schematic diagram illustrating a controller of a gas turbine system.
  • FIG. 3 is a graph showing an example of a temperature control curve.
  • FIG. 4 is a graph showing an example of a relationship between a specific heat ratio and a bias value.
  • FIG. 5 is a graph showing an example of a relationship between a specific heat ratio and a bias value.
  • FIG. 6 is a graph showing an example of a relationship between a specific heat ratio and a bias value.
  • FIG. 7 is a flowchart showing an example of a driving operation of the gas turbine system of the present embodiment.
  • FIG. 8 is a schematic diagram illustrating another example of a fuel gas supply mechanism.
  • FIG. 9 is a flowchart showing an example of a driving operation of a gas turbine system of another example.
  • FIG. 10 is a flowchart showing a modified example of a driving operation of a gas turbine system.
  • FIG. 11 is a flowchart showing a modified example of a driving operation of a gas turbine system.
  • FIG. 1 is a schematic configuration diagram representing a gas turbine system of the present embodiment.
  • a gas turbine system 10 includes a gas turbine 11 , a fuel gas supply mechanism 12 for supplying fuel gas to the gas turbine 11 , an air supply mechanism 13 for supplying air to the gas turbine 11 , an exhaust gas expelling mechanism 14 in which exhaust gas expelled from the gas turbine 11 flows, an operation information detection unit 16 for detecting various types of operation information of the gas turbine 11 , and a controller 18 for controlling an operation of each unit of the gas turbine system 10 on the basis of input settings, input instructions, results detected by the detection unit, and the like.
  • the gas turbine 11 includes a compressor (A/C) 21 , a combustor 22 , and a turbine (G/T) 23 , and the compressor 21 and the turbine 23 are linked by a rotating shaft 24 so as to be able to integrally rotate.
  • the compressor 21 and the combustor 22 are connected and the combustor 22 and the turbine 23 are connected.
  • the compressor 21 compresses air A taken in from the air supply mechanism 13 and changes the amount of the air A taken in by changing the angle of an inlet guide vane 21 a provided at the inlet of the compressor 21 .
  • the combustor 22 carries out combustion by mixing compressed air supplied from the compressor 21 and fuel gas L supplied from a fuel gas supply line 32 .
  • the turbine 23 is rotated by combustion gas generated by combusting the fuel gas L in the combustor 22 being supplied thereto.
  • the compressor 21 is provided with the inlet guide vane (IGV) 21 a which is able to adjust the extent of opening of an air intake port.
  • the compressor 21 increases the compressed air amount generated by the compressor 21 by increasing the extent of opening of the inlet guide vane 21 a and decreases the compressed air amount generated by the compressor 21 by reducing the extent of opening.
  • the turbine 23 is supplied with the compressed air compressed by the compressor 21 through a casing, and cools blades and the like by using this compressed air as cooling air.
  • the fuel gas supply mechanism 12 includes the fuel gas supply line 32 and a control valve 34 .
  • the fuel gas supply line 32 is a pipe for connecting a supply source for supplying fuel gas and the combustor 22 .
  • the fuel gas supply line 32 supplies fuel gas supplied from the supply source to the combustor 22 .
  • the control valve 34 is a valve provided with a mechanism for adjusting the extent of opening and is provided in the fuel gas supply line 32 .
  • the control valve 34 is able to adjust the flow rate of the fuel gas L supplied from the fuel gas supply line 32 to the combustor 22 by opening and closing or adjusting the extent of opening.
  • the air supply mechanism 13 is provided with an air supply line 36 .
  • One end of the air supply line 36 is opened to the atmosphere and the other is linked with the compressor 21 .
  • the air supply line 36 supplies the air A to the compressor 21 .
  • the exhaust gas expelling mechanism 14 is provided with an exhaust gas line 38 .
  • the exhaust gas line 38 is linked with the turbine 23 and exhaust gas passing through the turbine 23 (combustion gas passing through the turbine 23 ) is supplied to the exhaust gas line 38 .
  • the exhaust gas line 38 supplies exhaust gas to a mechanism for processing exhaust gas, for example, an exhaust heat recovery mechanism, a mechanism for removing toxic substances, or the like.
  • the operation information detection unit 16 includes a composition meter 50 , an exhaust gas thermometer 52 , a compressed air pressure gauge 54 , a fuel flow meter 56 , a barometer 59 , an inlet guide vane angle meter (an IGV opening extent meter) 70 , and a rotation speed meter 72 . Each of these units sends detected information to the controller 18 .
  • the composition meter 50 is provided in the fuel gas supply line 32 and detects the composition of the fuel gas flowing in the fuel gas supply line 32 .
  • composition meter 50 it is possible to use various types of measuring devices for measuring the composition of fuel gas, and it is possible to use a sensor which irradiates fuel gas with measuring light, detects absorption of the measuring light, and detects the target component on the basis of the absorption amount, or a sensor which detects the Raman scattering light of measuring light and detects the target component on the basis of the intensity of the Raman scattering light.
  • the composition meter 50 may be provided with separate sensors for detecting each of the components to be detected, or may detect all of the components of the fuel gas with one sensor. Here, it is sufficient if the composition meter 50 is able to detect the main components contained in the fuel gas, and the composition meter 50 does not necessarily need to detect minor components.
  • the exhaust gas thermometer 52 is provided in the exhaust gas line 38 and detects the temperature of the exhaust gas flowing in the exhaust gas line 38 , commonly called the exhaust temperature.
  • the compressed air pressure gauge 54 detects the pressure of compressed air flowing from the compressor 21 toward the combustor 22 .
  • the compressed air pressure gauge 54 measures the discharge pressure of the compressor 21 .
  • the fuel flow meter 56 is arranged between the control valve 34 of the fuel gas supply line 32 and the combustor 22 .
  • the fuel flow meter 56 measures the flow rate of the fuel gas passing through the control valve 34 and supplied to the combustor 22 .
  • the barometer 59 is a pressure gauge for detecting the atmospheric pressure.
  • the installation position of the barometer 59 is not particularly limited.
  • the inlet guide vane angle meter 70 is a measuring instrument for detecting the angle of the inlet guide vane 21 a provided at the inlet of the compressor 21 .
  • the rotation speed meter 72 is a measuring instrument for detecting the rotation speed of the gas turbine 11 . As the rotation speed meter 72 , an encoder provided in a shaft rotating coaxially with the rotating shaft 24 of the gas turbine 11 can be used.
  • FIG. 2 is a schematic diagram illustrating the controller of the gas turbine system.
  • FIG. 2 is an extract of a portion relating to a function for controlling the supply of the fuel gas, out of the functions of the controller 18 .
  • the controller 18 is provided with various types of functions which are necessary for control of the gas turbine system 10 apart from the function illustrated in FIG. 2 .
  • the operation processing unit 64 is provided with a central processing unit (CPU) and a buffer and is provided with a function for executing various types of operations by executing a program.
  • the operation processing unit 64 calculates the extent of opening of the control valve 34 on the basis of information on the composition of the fuel gas acquired by the composition information acquiring unit 60 , operation information acquired by the operation information acquiring unit 62 , and information stored in the storage unit 66 , and controls the flow rate of the fuel gas supplied to the combustor 22 . This point will be described later.
  • the storage unit 66 includes reference data 66 a and a bias value calculation table 66 b .
  • the reference data 66 a stores information on a temperature control curve in the case of the composition of the reference fuel gas.
  • FIG. 3 is a graph showing an example of the temperature control curve (a curve indicating a relationship between control setting values). Specifically, as shown in FIG. 3 , the temperature control curve is a function of the pressure of the compressed air and the exhaust temperature such that the inlet temperature of the turbine 23 is constant.
  • the compressor exhaust air pressure is substantially the turbine expansion ratio; however, as described above, considering that the inlet pressure of the turbine 23 is equal to the compressor exhaust air pressure apart from the pressure loss of the combustor 22 and that the outlet pressure of the turbine 23 is equal to the atmospheric pressure (approximately 1 atm) apart from the exhaust pressure loss, the pressure of compressed air (the pressure of the compressed air at a position measured by the compressed air pressure gauge 54 ) is used as a substitute for the turbine expansion ratio.
  • the exhaust temperature is the temperature of the exhaust gas (the temperature of the exhaust gas at a position measured by the exhaust gas thermometer 52 ). In the gas turbine system 10 , when the fuel composition does not change and is the same as the reference, it is possible to make the temperature of the combustion gas supplied to the turbine equal to a desired temperature by performing an operation under the conditions indicated by a temperature control curve 80 for that case.
  • K of the combustion gas is 1.4 and the temperature control curve in that case is the temperature control curve 80 .
  • the temperature control curve becomes a temperature control curve 82 .
  • the shift amount of the temperature control curve 82 from the temperature control curve 80 as a reference is a bias value 84 .
  • the bias value calculation table 66 b is a table storing the relationship between a specific heat ratio K of the combustion gas calculated from the composition of the fuel gas and a bias value for bias-correcting the temperature control curve 80 of the reference data.
  • the relationship in the bias value calculation table 66 b between the specific heat ratio K and the bias value may be calculated by an experiment or by simulation. Furthermore, the relationship is not necessarily such that the temperature of the combustion gas is constant with respect to changes in K of the combustion gas, and a different relationship may be used according to the purpose. In addition, a table is used in the present embodiment; however, simply, a function may be used, or, for example, a ratio of a bias value with respect to the shift amount described above may be stored. In a case where K is 1.5, the operation processing unit 64 calculates the temperature control curve 82 by calculating the bias value 84 from the bias value calculation table 66 b or from the function described above, and correcting the temperature control curve 80 with the bias value 84 . This point will be described later.
  • FIG. 4 to FIG. 6 are each a graph showing an example of a relationship between a specific heat ratio and a bias value.
  • FIG. 4 it is possible to make a relationship between the specific heat ratio K and a bias value to be stored in the bias value calculation table 66 b a relationship where the temperature adjustment bias is changed according to the specific heat ratio K such that the temperature of the combustion gas is constant without being affected by the specific heat ratio K of the combustion gas.
  • the controller 18 is able to reduce the changes in the temperature of the combustion gas which occur in a case where the specific heat ratio K of the combustion gas changes, by controlling the bias value using the relationship shown in FIG. 4 .
  • the bias value is a constant value X1 in a case where the specific heat ratio K of the combustion gas is equal to a reference value K or less, and that the temperature of the combustion gas is constant without being affected by the specific heat ratio K of the combustion gas in a case where the specific heat ratio K of the combustion gas is greater than the reference value K.
  • the controller 18 linearly changes the temperature adjustment bias according to the specific heat ratio K such that the temperature of the combustion gas is constant without being affected by the specific heat ratio K of the combustion gas in a case where the specific heat ratio K of the combustion gas is greater than the reference value K.
  • the controller 18 is able to carry out control such that the temperature is constant in a case where the composition of the fuel gas changes to the over-firing side.
  • the controller 18 sets the bias value to the constant value X1 in a case where the specific heat ratio K of the combustion gas is equal to the reference value K or less.
  • the bias value is the constant value X1 in a case where the specific heat ratio K of the combustion gas is equal to the reference value K or less and the bias value is a constant value X2 in a case where the specific heat ratio K of the combustion gas is greater than the reference value K.
  • X2 is a smaller value than X1, that is, X2 ⁇ X1.
  • the bias value is switched according to whether the specific heat ratio K of the combustion gas is greater than the reference value K or is equal to the reference value K or less, it is possible to perform combustion under conditions where there is less risk that over-firing may occur by reducing the bias value when a state is reached where the specific heat ratio K of the combustion gas is high and over-firing is likely to occur if the combustion conditions remain the same.
  • the bias value is switched in two stages on the basis of the specific heat ratio K of the combustion gas; however, there may be three or more stages.
  • the control valve control unit 68 controls the control valve 34 on the basis of the extent of opening of the control valve 34 calculated by the operation processing unit 64 .
  • FIG. 7 is a flowchart showing an example of a driving operation of the gas turbine system of the present embodiment.
  • the controller 18 repeatedly executes the process shown in FIG. 7 during the operation of the gas turbine 11 .
  • the controller 18 acquires operation information and the composition of the fuel gas (Step S 12 ).
  • the controller 18 acquires information on the composition of the fuel gas with the composition information acquiring unit 60 and acquires various types of operation information with the operation information acquiring unit 62 .
  • the controller 18 calculates the feed rate of the air on the basis of the angle of the inlet guide vane 21 a detected by the inlet guide vane angle meter 70 , the intake temperature, and the rotation speed of the compressor detected by the rotation speed meter 72 , and additionally calculates the air-fuel ratio on the basis of the feed rate of the fuel gas and the feed rate of the air.
  • the controller 18 detects the composition of the combustion gas on the basis of the composition of gas generated in a case where fuel gas is completely combusted, and the air-fuel ratio. In other words, the ratio of surplus air which does not contribute to combustion is calculated on the basis of the air-fuel ratio and the composition of the combustion gas is calculated assuming that the gas generated in a case where fuel gas is completely combusted is diluted with the surplus air.
  • the controller 18 calculates K of the combustion gas on the basis of the composition of the combustion gas (Step S 14 ). Specifically, K of each component of the combustion gas is extracted on the basis of the composition of the combustion gas. After that, the specific heat ratio of the combustion gas is calculated on the basis of the specific heat ratio of the components contained in the combustion gas and the ratio of each of the components of the combustion gas. As the calculation method, it is possible to carry out calculation using a weighted average on the basis of the concentration of each of the components.
  • the controller 18 determines the bias value on the basis of the specific heat ratio K of the combustion gas (Step S 16 ). Specifically, the controller 18 reads out the bias value calculation table 66 b and determines a bias value corresponding to the specific heat ratio K of the combustion gas on the basis of the bias value calculation table 66 b and the calculated specific heat ratio K of the combustion gas.
  • the controller 18 After determining the bias value, the controller 18 corrects a function of the compressed air pressure and the exhaust gas temperature using the bias value (Step S 18 ). In other words, the controller 18 obtains a corrected temperature control curve by adding the bias value to the reference temperature control curve.
  • the controller 18 determines a fuel control value (a value used for controlling the feed rate of the fuel gas) on the basis of the corrected temperature control curve (function) and operation information (Step S 20 ). Specifically, in FIG. 3 , a set of the measured compressed air pressure and exhaust gas temperature is plotted, and the fuel control value is determined such that the fuel flow rate is decreased in a case where the set is above and to the right of the corrected temperature control curve and that the fuel flow rate is increased in a case where the set is below left.
  • the control valve 34 is controlled on the basis of the fuel control value determined by the control valve control unit 68 (Step S 22 ), and the present process ends.
  • the fuel control value may be information on a value indicating the extent of opening of the control valve 34 or information on the amount of change in the extent of opening.
  • the gas turbine system 10 detects the composition of the fuel gas, calculates the specific heat ratio K of the combustion gas on the basis of the composition of the fuel gas, calculates a bias value on the basis of a relationship set beforehand, and corrects the temperature control curve using the bias value.
  • the gas turbine system 10 is able to set the relationship between the exhaust temperature and the temperature of the combustion gas at the turbine inlet so as to correspond to the composition of the fuel gas.
  • the gas turbine system 10 by controlling the operation conditions (the feed rate of the fuel gas in the present embodiment) on the basis of the corrected temperature control curve, it is possible to reduce the difference between the predicted temperature of the combustion gas at the turbine inlet and the actual temperature. Accordingly, it is possible to control the gas turbine system 10 with higher precision and to operate the gas turbine system 10 with a higher output and efficiency. Specifically, when the temperature control curve is controlled using the calories of the fuel gas, control is carried out using the same temperature control curve for fuel gases whose compositions are different even though the calories are the same. By contrast, when the composition of the fuel gas changes, the gas turbine system 10 of the present embodiment is able to calculate K of the combustion gas corresponding to the composition of the fuel gas and correct the temperature control curve.
  • the gas turbine system 10 is able to bring the target temperature close to the maximum allowable temperature of the gas turbine 11 by being able to reduce error between the target temperature of the combustion gas at the turbine inlet and the actual temperature. Therefore, it is possible to efficiently operate the gas turbine system 10 .
  • the gas turbine system 10 is able to reduce changes in the actual temperature by calculating a bias value, for example, using the relationship shown in FIG. 4 , and to reduce the risk that over-firing may occur, as well as to perform an operation while maintaining a state of being close to the maximum allowable temperature even in a case where the specific heat ratio K of the combustion gas changes.
  • the gas turbine system 10 is able to appropriately control the temperature in a case where the specific heat ratio K of the combustion gas changes to the over-firing side relative to the reference value K by calculating a bias value, for example, using the relationship shown in FIG. 4 , and to reduce the risk that over-firing may occur.
  • the temperature control curve is a function of the compressed air pressure and the exhaust temperature; however, the turbine expansion ratio may be used in place of the compressed air pressure.
  • the compressed air pressure may be used as a substitute for the turbine inlet pressure in order to determine the turbine expansion ratio, or the atmospheric pressure may be used as a substitute for the turbine exhaust pressure.
  • the fuel being gas; however, it is clear that the form of the fuel is essentially not limited to a gas and the fuel may be, for example, liquid fuel.
  • FIG. 8 is a schematic diagram illustrating another example of a fuel gas supply mechanism.
  • a gas turbine system 10 a illustrated in FIG. 8 is the same as the gas turbine system 10 apart from the configuration on the upstream side of the fuel gas supply line 32 . Description will be given of the configuration unique to the gas turbine system 10 a.
  • a fuel gas supply mechanism 12 a includes a first fuel gas supply line 102 through which a fuel gas L 1 is supplied, a second fuel gas supply line 104 through which a fuel gas L 2 is supplied, a control valve 106 provided in the first fuel gas supply line 102 , and a control valve 108 provided in the second fuel gas supply line 104 .
  • the fuel gas supply mechanism 12 a supplies the fuel gas L 1 from the first fuel gas supply line 102 to the fuel gas supply line 32 and supplies the fuel gas L 2 from the second fuel gas supply line 104 to the fuel gas supply line 32 .
  • control valves 106 and 108 which are able to adjust the flow rates of the first fuel gas supply line 102 and the second fuel gas supply line 104 are provided; however, the control valves 106 and 108 need not be provided.
  • the fuel gas L 1 and the fuel gas L 2 in the present embodiment are fuel gases whose composition is known.
  • An operation information detection unit 16 a also includes a fuel flow meter 112 provided in the first fuel gas supply line 102 and a fuel flow meter 114 provided in the second fuel gas supply line 104 .
  • the fuel flow meters 112 and 114 calculate the fuel flow rates of the lines provided with these fuel flow meters.
  • FIG. 9 is a flowchart showing an example of a driving operation of a gas turbine system of another example.
  • the operation shown in FIG. 9 may be performed by the controller 18 , or may be performed by providing a separate operation apparatus.
  • the controller 18 performs the operation in the present embodiment.
  • the controller 18 acquires the compositions of each fuel gas, that is, the fuel gases L 1 and L 2 (Step S 30 ), acquires a balance between the flow rates of the fuel gases from the fuel flow meters 112 and 114 (Step S 32 ), calculates the composition of the mixed fuel gas on the basis of the balance between the flow rates and the compositions of the fuel gases (Step S 34 ), and ends the present process.
  • the balance between the flow rates it is sufficient if a relative balance is acquired, and the flow rates may be acquired or a flow rate ratio may be detected.
  • the gas turbine system 10 a in a case where the composition of the fuel gas is known or in a case where such can be regarded as known, it is possible to calculate the composition of the fuel gas supplied to the combustor without detecting the composition of the fuel gas using a composition meter. In addition, it is possible to simplify the configuration of the apparatus by not using a composition meter. In addition, the gas turbine system 10 a mixes two types of fuel gas; however, the number of fuel gases to be mixed is not particularly limited.
  • the gas turbine systems 10 and 10 a set a reference value with respect to the composition of the fuel gas, and switch controls to be executed according to whether or not the composition of the fuel gas has changed to the over-firing side relative to the reference value.
  • the gas turbine systems 10 and 10 a set a reference value with respect to K which is a specific heat ratio calculated on the basis of the composition of the fuel gas, and switch controls to be executed between a case where K has changed to the over-firing side relative to the reference value, in other words, a case where K has increased, and a case where K has changed to the opposite side to the over-firing side, in other words, a case where K has decreased.
  • the controller 18 calculates a bias value and executes control (decreases the bias) on the basis of the bias value, and in a case where K has decreased to the reference value or less, the controller 18 does not execute control for changing the bias value (does not increase the bias).
  • FIG. 10 is a flowchart showing a modified example of a driving operation of a gas turbine system. Description will be given below of the case of the gas turbine system 10 ; however, the same applies to the case of the gas turbine system 10 a or a gas turbine system of another example.
  • the controller 18 executes the process shown in FIG. 10 as a process for determining the bias value on the basis of the composition of the fuel gas, for example, the process of Step S 14 and Step S 16 in the flowchart in FIG. 7 .
  • the controller 18 calculates the specific heat ratio K of the combustion gas on the basis of the composition of the fuel gas (Step S 42 ). After calculating the specific heat ratio K of the combustion gas, the controller 18 determines whether the calculated specific heat ratio K of the combustion gas is higher than the reference value (Step S 44 ). In a case where it is determined that the specific heat ratio K is higher than the reference value (Yes in Step S 44 ), the controller 18 sets the bias value on the basis of the specific heat ratio K (Step S 46 ). In this case, since the specific heat ratio K is higher than the reference value, the bias value is decreased.
  • Step S 48 the controller 18 does not change the bias value.
  • the specific heat ratio K is equal to the reference value or less, the combustion temperature of the combustor 22 is decreased due to the temperature adjustment control compared to a case where the specific heat ratio K is equal to the reference value. Therefore, it is possible to operate the combustor 22 in a safer state.
  • the gas turbine system 10 is able to execute control which does not make the bias value higher than the reference value by executing control for adjusting the bias value only in a case where the composition of the fuel gas changes to the over-firing side. Thus, it is possible to safely operate the gas turbine system 10 .
  • the gas turbine system 10 sets a reference value with respect to K which is a specific heat ratio calculated on the basis of the composition of the fuel gas, and quickly executes a process for decreasing the bias value in a case where K has changed to the over-firing side, in other words, a case where K has increased, and executes a process for increasing the bias value to match the arrival time of the fuel gas in a case where K has changed to the opposite side to the over-firing side, in other words, a case where K has decreased.
  • the gas turbine system 10 is able to shift the timing for adjusting the extent of opening of the control valve by shifting the timing for executing a process on the basis of changes in the bias value.
  • FIG. 11 is a flowchart showing a modified example of a driving operation of a gas turbine system.
  • the controller 18 executes the process shown in FIG. 11 as a process for executing the control of the control valve, for example, the process of Step S 22 in FIG. 7 .
  • the controller 18 determines whether the calculated specific heat ratio K has increased (Step S 52 ).
  • the controller 18 executes control of the control valve 34 without providing a waiting time (Step S 54 ) in a case where it is determined that the specific heat ratio K has increased (Yes in Step S 52 ). In this case, the controller 18 controls the control valve 34 so as to achieve the determined control value at the time when a control value is determined.
  • the controller 18 executes control of the control valve 34 while taking the arrival time of the fuel gas into consideration (Step S 56 ). In this case, the controller 18 controls the control valve 34 so as to achieve the determined control value at the time when the measured fuel gas arrives at the control valve 34 .
  • the gas turbine system 10 is able to appropriately control the combustion conditions in the combustor 22 while maintaining a high level of safety by shifting the timing for adjusting the extent of opening of the control valve by shifting the timing for executing the process on the basis of changes in the bias value. Specifically, it is possible to prevent over-firing and thereby to prevent damage to the combustor 22 by quickly executing the process for decreasing the bias value in a case where K has increased and, in contrast, it is possible to prevent changes in the gas turbine output due to changes in the combustion temperature by executing the process for increasing the bias value to match the arrival time of the fuel gas in a case where K has decreased.
  • the gas turbine system 10 decreases the bias value in a case where it is detected that the composition meter 50 is abnormal.
  • FIG. 12 is a flowchart showing a modified example of a driving operation of the gas turbine system. It is preferable that the controller 18 executes the control shown in FIG. 12 in parallel with the various types of controls described above.
  • the controller 18 determines whether an abnormality in the composition meter 50 was detected (Step S 62 ).
  • the controller 18 determines that the composition meter 50 is abnormal in a case where a signal providing notification of the occurrence of an abnormality, which is output from the composition meter 50 , is detected or in a case of being unable to acquire a measurement result from the composition meter 50 .
  • the controller 18 sets the bias value to a bias value on the safer side (Step S 64 ) in a case where it is determined that an abnormality in the composition meter 50 was detected (Yes in Step S 62 ). In other words, the controller 18 further decreases the bias value and changes conditions so as to decrease the output.
  • the controller 18 ends the process directly in a case where it is determined that no abnormality in the composition meter 50 is detected (No in Step S 62 ).
  • the gas turbine system 10 can be more safely operated, as the gas turbine system 10 sets the bias value to a value for operating under safer conditions in a case where an abnormality in the composition meter 50 is detected.
  • FIG. 13 is a schematic configuration diagram representing a gas turbine system of another example.
  • a gas turbine system 10 b illustrated in FIG. 13 is also the same as the gas turbine system 10 apart from the configuration on the upstream side of the fuel gas supply line 32 .
  • the gas turbine system 10 b is a blast furnace gas (BFG) firing gas turbine system and BFG is supplied as a fuel gas L 1 a and coke oven gas (COG) is supplied as a fuel gas L 2 a.
  • BFG blast furnace gas
  • COG coke oven gas
  • a fuel gas supply mechanism 12 b of the gas turbine system 10 b includes a first fuel gas supply line 120 for supplying the fuel gas L 1 a , a second fuel gas supply line 122 for supplying the fuel gas L 2 a , a mixer 124 for mixing the fuel gas L 1 a supplied from the first fuel gas supply line 120 and the fuel gas L 2 a supplied from the second fuel gas supply line 122 , a mixed fuel line 126 which guides the fuel gas mixed in the mixer 124 and is linked with the fuel gas supply line 32 , a gas compressor (G/C) 128 arranged in the mixed fuel line 126 , which compresses the mixed fuel gas and increases the pressure, a bypass line 130 which is branched from a part linking the fuel gas supply line 32 and the mixed fuel line 126 and linked with the upstream side of the mixed fuel line 126 , a cooler 132 provided in the bypass line 130 , and a bypass control valve 140 arranged in the bypass line 130 between the part linking the fuel gas supply line 32 and the mixed fuel line 126
  • the fuel gas L 1 a supplied from the first fuel gas supply line 120 and the fuel gas L 2 a supplied from the second fuel gas supply line 122 are mixed by the mixer 124 and supplied to the mixed fuel line 126 .
  • the fuel gas supplied to the mixed fuel line 126 is increased in pressure by the gas compressor 128 and supplied to the fuel gas supply line 32 .
  • the fuel gas supply mechanism 12 b as it is provided with the bypass line 130 , a part of the fuel gas in the mixed fuel line 126 flows into the bypass line 130 in a case where the bypass control valve 140 is open.
  • the fuel gas flowing into the bypass line 130 is supplied to the mixed fuel line 126 after being cooled by the cooler 132 to the same pressure as the mixed fuel gas before being increased in pressure.
  • the fuel gas supply mechanism 12 b controls the flow rate of the fuel gas supplied to the combustor 22 by controlling the flow rate of the fuel gas circulating in the bypass line 130 using the bypass control valve 140 .
  • the fuel gas supply mechanism 12 b is able to continuously supply the gas turbine 11 with fuel gas increased in pressure to a predetermined pressure while reducing the load applied to the gas turbine 11 by circulating a part of the fuel gas.
  • a composition meter 50 a is provided in the mixed fuel line 126 .
  • a controller 18 a controls the flow rate of the fuel gas supplied to the combustor 22 by determining the feed rate of the fuel gas in the same manner as for the controller 18 on the basis of the composition of the mixed fuel gas detected by the composition meter 50 a , and controlling the extent of opening of the bypass control valve 140 on the basis of the determination.
  • the gas turbine system 10 b is able to control the output of a gas turbine with high precision by detecting the composition of the fuel gas and correcting the temperature control curve on the basis of K of the combustion gas even in a case where changes in the characteristics of the fuel gas are large, such as in a BFG firing gas turbine system.
  • the composition meter 50 a is provided in the mixed fuel line 126 in the present embodiment; however, the position at which the composition meter 50 a is provided is not limited thereto.
  • the composition meter 50 a may be provided in the fuel gas supply line 32 or may be provided in the bypass line 130 .
  • a control valve may be provided in the fuel gas supply line 32 to control the extent of opening of the control valve.
  • an apparatus such as an electric dust collector may be provided in the mixed fuel line 126 to remove foreign matter contained in the fuel.
  • two types of fuel gas are mixed in the present embodiment; however, three or more types of fuel may be mixed.
  • the gas turbine system of the present embodiment for a low calorie gas firing gas turbine system where changes in the calorie setting occur, in addition to a BFG firing gas turbine system.
  • the gas turbine system of the present embodiment is able to obtain remarkable effects when applied to a system where the calories of the fuel gas are low, the flow rate of the fuel gas is high, and the composition of the fuel gas may change such as the BFG firing gas turbine system or the low calorie gas firing gas turbine system described above.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Turbines (AREA)
US14/760,787 2013-02-26 2014-02-24 Gas turbine system, controller, and gas turbine operation method Active 2035-04-04 US9856795B2 (en)

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PCT/JP2014/054375 WO2014132932A1 (ja) 2013-02-26 2014-02-24 ガスタービンシステム、制御装置及びガスタービンの運転方法

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EP2840245A1 (en) * 2013-08-20 2015-02-25 Alstom Technology Ltd Method for controlling a gas turbine group
US10982599B2 (en) 2015-12-04 2021-04-20 Powerphase International, Llc Gas turbine firing temperature control with air injection system
JP6706936B2 (ja) * 2016-03-09 2020-06-10 三菱日立パワーシステムズ株式会社 ガスタービンの制御装置及びガスタービンの制御方法
JP6786233B2 (ja) * 2016-03-22 2020-11-18 三菱パワー株式会社 ガスタービンの特性評価装置及びガスタービンの特性評価方法
JP6673733B2 (ja) * 2016-03-28 2020-03-25 三菱日立パワーシステムズ株式会社 圧縮機の修正回転数算出方法、圧縮機の制御方法、これらの方法を実行する装置、及びこの装置を備えるガスタービンプラント
KR101985353B1 (ko) * 2018-03-27 2019-06-03 두산중공업 주식회사 연료 조성에 따른 가스 터빈 제어 시스템 및 방법
US11125169B2 (en) * 2018-12-19 2021-09-21 General Electric Company Fuel system for heat engine
CN110925107B (zh) * 2019-12-20 2022-02-22 潍柴西港新能源动力有限公司 一种燃气发电发动机燃料闭环控制方法
JP7269204B2 (ja) 2020-09-28 2023-05-08 三菱重工業株式会社 ガスタービン及びその燃料流量調整方法
CN113466691B (zh) * 2021-06-18 2022-02-22 哈尔滨工程大学 一种两阶段压缩膨胀发电机发电效率的预测方法
GB2617309A (en) * 2021-12-21 2023-10-11 Rolls Royce Plc Aircraft fuel management

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US20150354466A1 (en) 2015-12-10
KR101690444B1 (ko) 2016-12-27
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JPWO2014132932A1 (ja) 2017-02-02
KR20150099865A (ko) 2015-09-01
JP6005252B2 (ja) 2016-10-12
DE112014001000T5 (de) 2015-11-12
WO2014132932A1 (ja) 2014-09-04

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